Aircraft multi-section common static test fixture

Abstract

The utility model discloses a kind of static test tooling of multiple section sharing of aircraft, including support, base, three support top beams, mounting base assembly and mounting support assembly. Support includes rectangular bottom frame, four supporting legs and rectangular top frame arranged from bottom to top, base includes several bottom plates, bottom plate is fixed in the rectangular bottom frame lower end surface of support, three support top beams are fixedly arranged on the rectangular top frame upper end surface of support, mounting base assembly includes four first mounting seat, two second mounting seat and a third mounting seat, mounting support assembly includes flat tail mounting support, two section mounting supports and two vertical tail mounting supports, the utility model is the static test tooling of multiple section sharing, switching section in test only needs to disassemble and assemble a small amount of components, main body structure does not need to adjust. It can reduce tooling manufacturing cost, greatly save dismounting manpower and working hours, significantly improve test efficiency and economy.

Description

Technical Field

[0001] This utility model relates to the field of test fixture technology, specifically to a static test fixture for multiple sections of an aircraft. Background Technology

[0002] As an indispensable core component of an aircraft, the stiffness of the wing is directly related to the aircraft's flight performance, stability, and even operational safety. The static test of the wing is a key means of measuring its stiffness performance. The core objective of this test is to accurately measure the degree and shape of deformation of the wing when it is subjected to specific loads, and to evaluate its stiffness performance using numerical analysis and other technical means.

[0003] For medium to large-sized unmanned and manned aircraft, static tests are conducted after the structural components are assembled to verify that the structure meets the design requirements. Static tests on aircraft components are generally conducted in two ways: one is to conduct the test on the aircraft after complete assembly, and the other is to conduct a separate static test on each component. The first method requires designing relatively large tooling to protect the airframe, which is complex and costly. The second method requires designing separate tooling for each component to securely connect them, such as the static test tooling described in Reference 1.

[0004] Reference 1: Chinese patent document with publication number CN 222973636 U.

[0005] Reference 1 describes a static testing fixture for a small aircraft wing, including a support frame. Load positions and angle control positions are respectively set on both sides of the support frame. The horizontal height of the load positions is higher than that of the angle control positions. An angle control frame is set on the angle control positions and connected to the wing. Adjusting the angle between the wing and the horizontal plane allows for the adjustment of the wing's horizontal angle, simulating the actual state of the wing in flight and thus improving the accuracy of static force measurement.

[0006] The aforementioned test fixture is only for static testing of the fixed wing section. When testing one section and then another, the fixture needs to be changed or disassembled and reassembled, which is inefficient. Utility Model Content

[0007] The purpose of this utility model is to solve the above-mentioned technical problems existing in the prior art and to provide a static test fixture for multiple sections of an aircraft.

[0008] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is: a static test fixture for multiple sections of an aircraft, including a support, a base, three supporting top beams, a mounting base assembly, and a mounting support assembly;

[0009] The support includes a rectangular base frame, four legs, and a rectangular top frame arranged from bottom to top, with the four legs distributed at the four corners of the support.

[0010] The base includes several base plates, which are fixed to the lower end face of the rectangular base frame of the support, and part of the base plate extends to the outside of the rectangular base frame.

[0011] The three supporting beams are fixedly installed on the upper surface of the rectangular top frame of the support. The rectangular top frame includes two first sides and two second sides. The supporting beams are installed between the two first sides and are parallel to each other.

[0012] The mounting base assembly includes four first mounting seats, two second mounting seats, and one third mounting seat. The four first mounting seats are symmetrically arranged on two outer support beams, and the second and third mounting seats are fixedly arranged on the middle support beam, with the third mounting seat located between the two second mounting seats.

[0013] The mounting support assembly includes a horizontal tail mounting support, two section mounting supports, and two vertical tail mounting supports. The horizontal tail mounting support can be detachably fixed to a second mounting base. The two section mounting supports can be detachably fixed to the first mounting bases of the two supporting top beams, respectively. The two vertical tail mounting supports can be detachably fixed to a third mounting base.

[0014] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: bolt mounting holes are provided on the plate extending to the outside of the rectangular base frame.

[0015] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: the support also includes a horizontal reinforcing rod and two vertical reinforcing rods. The horizontal reinforcing rod is set inside the rectangular top frame, and its two ends are fixedly connected to the two second sides of the rectangular top frame respectively. The two vertical reinforcing rods are symmetrically set at both ends of the rectangular top frame. The top of the vertical reinforcing rod is fixedly connected to the second side of the rectangular top frame, and the bottom of the vertical reinforcing rod is fixedly connected to the rectangular bottom frame.

[0016] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: the support is composed of welded rectangular steel pipes.

[0017] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: the first mounting base, the second mounting base and the third mounting base are all rectangular plate structures, and the length directions of the first mounting base and the second mounting base are perpendicular to the length direction of the supporting top beam, while the length direction of the third mounting base is parallel to the length direction of the supporting top beam.

[0018] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: the first mounting base and the second mounting base are each provided with four fixing holes, which are distributed at the corners; the third mounting base is provided with eight fixing holes, which are symmetrically distributed on the long side of the third mounting base.

[0019] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: the horizontal stabilizer mounting bracket includes a base plate and a side plate. The side plate is vertically fixed on the base plate. The side plate is a rectangular plate with its long side parallel to the base plate. The side plate has two mounting holes from left to right.

[0020] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: the section mounting support includes a base plate and a side plate. The side plate is vertically fixed on the base plate. The side plate is a rectangular plate with its short side parallel to the base plate. A mounting hole is provided on the side plate.

[0021] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: the vertical tail mounting support includes a base plate and a side plate. The side plate is vertically fixed on the base plate. The side plate is a long strip plate with its short side parallel to the base plate. The side plate has two mounting holes from top to bottom.

[0022] As a further optimization of the static test fixture for multiple sections of an aircraft according to this utility model: a reinforcing plate is provided between the side plate and the bottom plate.

[0023] This invention offers the following advantages: It is a static testing fixture shared by multiple sections. When conducting static tests using this fixture, only a small number of components need to be disassembled and reassembled during the transition from one section's test to the next, without requiring adjustments to the main structure of the fixture. This effectively reduces the overall manufacturing cost of the fixture while significantly saving manpower and time spent on disassembly and reassembly, thus significantly improving testing efficiency and economy. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the static testing fixture of this utility model;

[0025] Figure 2 A schematic diagram of the structure during a static test of the tail section;

[0026] Figure 3 A schematic diagram of the structure during a static test of the tail section;

[0027] Figure 4 A schematic diagram of the structure during static testing of the wing section;

[0028] Marked in the image:

[0029] 1. Support;

[0030] 101. Rectangular base frame;

[0031] 102. Support leg;

[0032] 103. Rectangular top frame;

[0033] 2. Base;

[0034] 3. Support the top beam;

[0035] 4. Install the base assembly;

[0036] 401. First mounting bracket;

[0037] 402. Second mounting bracket;

[0038] 403. Third mounting bracket;

[0039] 501. Flat-tail mounting bracket;

[0040] 502. Sectional installation supports;

[0041] 503. Tail support;

[0042] 6. Horizontal reinforcing bar;

[0043] 7. Vertical reinforcing bar;

[0044] 8. Flat-tail section;

[0045] 9. Tail section;

[0046] 10. Wing section. Detailed Implementation

[0047] To better understand this utility model, the following embodiments further illustrate the content of this utility model, but the content of this utility model is not limited to the following embodiments.

[0048] As shown in the figure: A common static test fixture for multiple sections of an aircraft includes a support 1, a base 2, three supporting beams 3, a mounting base assembly 4, and a mounting support assembly.

[0049] The support 1 includes a rectangular base frame 101, four legs 102, and a rectangular top frame 103 arranged from bottom to top. The four legs 102 are distributed at the four corners of the support 1. The support 1 also includes a horizontal reinforcing rod 6 and two vertical reinforcing rods 7. The horizontal reinforcing rod 6 is disposed inside the rectangular top frame 103, and its two ends are fixedly connected to the two second sides of the rectangular top frame 103, respectively. The two vertical reinforcing rods 7 are symmetrically disposed at both ends of the rectangular top frame 103. The top of the vertical reinforcing rods 7 is fixedly connected to the second side of the rectangular top frame 103, and the bottom of the vertical reinforcing rods 7 is fixedly connected to the rectangular base frame 101.

[0050] Support 1, as the basic supporting component of the tooling, adopts a layered frame structure design. From bottom to top, it consists of three core parts: a rectangular base frame 101, four legs 102, and a rectangular top frame 103. The rectangular base frame 101 serves as the bottom load-bearing foundation of the entire support, providing a stable installation reference for the subsequent structure. The four legs 102 are respectively installed at the four corners of support 1, with their lower ends fixedly connected to the four corners of the rectangular base frame 101, and their upper ends extending vertically upwards and connecting to the four corners of the rectangular top frame 103, forming vertical support for the top structure and ensuring the three-dimensional stability of the entire support frame.

[0051] To further enhance the structural strength and deformation resistance of support 1, the support is additionally equipped with a horizontal reinforcing rod 6 and two vertical reinforcing rods 7 as auxiliary support structures. Specifically, the horizontal reinforcing rod 6 is horizontally arranged in the internal area of ​​the rectangular top frame 103, and its length matches the horizontal span of the rectangular top frame 103. Its two ends are fixedly connected to the two opposite second sides of the rectangular top frame 103, which enhances the planar stiffness of the rectangular top frame 103 through the horizontal tie effect and prevents the top frame from undergoing lateral deformation under stress. The two vertical reinforcing rods 7 are symmetrically distributed at both ends of the rectangular top frame 103. Each vertical reinforcing rod 7 is arranged in the vertical direction, and its top is firmly connected to the corresponding second side of the rectangular top frame 103. Its bottom extends downward to the rectangular bottom frame 101 and is fixed thereto, forming a longitudinal reinforcing structure that runs through the top frame and the bottom frame, further enhancing the overall longitudinal bearing capacity and anti-overturning performance of the support.

[0052] All structural components of support 1 are made of rectangular steel tubes. The components are connected in an integrated manner through welding. This not only ensures the connection strength of each node, but also allows the entire support frame to have high strength while also being simple in structure and lightweight, thanks to the regular cross-sectional characteristics of the rectangular steel tubes, thus meeting the support stability requirements during subsequent use.

[0053] Considering that the test ground may have some uneven areas, a base 2 is added to the lower part of the main fixture to avoid these uneven areas and increase the stability of the fixture. The base also has pre-drilled bolt holes for connecting expansion bolts to the ground, further increasing the fixture's stability. The base 2 includes several base plates, which are fixed to the lower end face of the rectangular base frame 101 of the support 1. Part of the base plate extends to the outside of the rectangular base frame 101; bolt holes are provided on the plate extending to the outside of the rectangular base frame 101.

[0054] Three supporting beams 3 are fixedly installed on the upper surface of the rectangular top frame 103 of the support 1. The rectangular top frame 103 includes two first sides and two second sides. The supporting beams 3 are installed between the two first sides and are parallel to each other.

[0055] The mounting base assembly 4 includes four first mounting bases 401, two second mounting bases 402 and one third mounting base 403. The four first mounting bases 401 are symmetrically arranged on the two outer support beams 3. The second mounting bases 402 and the third mounting base 403 are fixedly arranged on the middle support beam 3, and the third mounting base 403 is located between the two second mounting bases 402.

[0056] The first mounting base 401, the second mounting base 402, and the third mounting base 403 are all rectangular plate structures. The length directions of the first mounting base 401 and the second mounting base 402 are perpendicular to the length direction of the supporting top beam 3, and the length direction of the third mounting base 403 is parallel to the length direction of the supporting top beam 3.

[0057] Both the first mounting base 401 and the second mounting base 402 are provided with four fixing holes, which are distributed at the corners. The third mounting base 403 is provided with eight fixing holes, which are symmetrically distributed on the long side of the third mounting base 403.

[0058] The mounting bracket assembly includes a horizontal tail mounting bracket 501, two section mounting brackets 502, and two vertical tail mounting brackets 503. The horizontal tail mounting bracket 501 can be detachably fixed to the second mounting base 402. The two section mounting brackets 502 can be detachably fixed to the first mounting base 401 of the two supporting top beams 3 respectively. The two vertical tail mounting brackets 503 can be detachably fixed to the third mounting base 403.

[0059] The horizontal tail mounting bracket 501 includes a base plate and a side plate. The side plate is vertically fixed to the base plate and is rectangular, with its long side parallel to the base plate. The side plate has two mounting holes from left to right. The section mounting bracket 502 includes a base plate and a side plate. The side plate is vertically fixed to the base plate and is rectangular, with its short side parallel to the base plate. The side plate has one mounting hole. The vertical tail mounting bracket 503 includes a base plate and a side plate. The side plate is vertically fixed to the base plate and is elongated, with its short side parallel to the base plate. The side plate has two mounting holes from top to bottom. Reinforcing plates are provided between the side plates and the base plate.

[0060] like Figure 2 As shown, when a static load test is required on the horizontal tail section 8, a horizontal tail mounting bracket is installed on the tooling, and the mounting bracket is connected to the horizontal tail section. After that, a static load test can be performed on the horizontal tail section.

[0061] like Figure 3 As shown, when a static load test is required on the tail section 9, a tail mounting bracket is installed on the main fixture, and the mounting bracket is connected to the tail section. Then, a static load test can be performed on the tail section.

[0062] like Figure 4 As shown, this is the static test fixing method for wing section 10 of a certain type of aircraft. If other aircraft models need to undergo static tests later, such as changes in the distance and size of the mounting holes, only the matching section connection support needs to be replaced, and the entire tooling body can continue to be used.

[0063] The specific embodiments of this utility model have been described above. It should be understood that this utility model is not limited to the specific embodiments described above, and those skilled in the art can make various modifications or variations within the scope of the claims, which do not affect the substantive content of this utility model.

Claims

1. A static testing fixture for multiple sections of an aircraft, characterized in that: Includes a support (1), a base (2), three supporting top beams (3), a mounting base assembly (4), and a mounting support assembly; The support (1) includes a rectangular bottom frame (101), four legs (102) and a rectangular top frame (103) arranged from bottom to top, with the four legs (102) distributed at the four corners of the support (1); The base (2) includes several base plates, which are fixed to the lower end face of the rectangular base frame (101) of the support (1), and part of the base plate extends to the outside of the rectangular base frame (101). The three supporting beams (3) are fixedly installed on the upper surface of the rectangular top frame (103) of the support (1). The rectangular top frame (103) includes two first sides and two second sides. The supporting beams (3) are erected between the two first sides and are parallel to each other. The mounting base assembly (4) includes four first mounting seats (401), two second mounting seats (402) and one third mounting seat (403). The four first mounting seats (401) are symmetrically arranged on the two outer support beams (3). The second mounting seats (402) and the third mounting seat (403) are fixedly arranged on the middle support beam (3), and the third mounting seat (403) is located between the two second mounting seats (402). The mounting bracket assembly includes a horizontal tail mounting bracket (501), two section mounting brackets (502), and two vertical tail mounting brackets (503). The horizontal tail mounting bracket (501) can be detachably fixed to the second mounting base (402). The two section mounting brackets (502) can be detachably fixed to the first mounting base (401) of the two supporting top beams (3), respectively. The two vertical tail mounting brackets (503) can be detachably fixed to the third mounting base (403).

2. The shared static testing fixture for multiple aircraft sections as described in claim 1, characterized in that: Bolt mounting holes are provided on the plate extending to the outside of the rectangular base frame (101).

3. The shared static testing fixture for multiple aircraft sections as described in claim 1, characterized in that: The support (1) also includes a horizontal reinforcing rod (6) and two vertical reinforcing rods (7). The horizontal reinforcing rod (6) is set inside the rectangular top frame (103), and its two ends are fixedly connected to the two second sides of the rectangular top frame (103). The two vertical reinforcing rods (7) are symmetrically set at both ends of the rectangular top frame (103). The top of the vertical reinforcing rod (7) is fixedly connected to the second side of the rectangular top frame (103), and the bottom of the vertical reinforcing rod (7) is fixedly connected to the rectangular bottom frame (101).

4. The shared static testing fixture for multiple aircraft sections as described in claim 1, characterized in that: The support (1) is composed of rectangular steel pipes welded together.

5. The shared static testing fixture for multiple aircraft sections as described in claim 1, characterized in that: The first mounting base (401), the second mounting base (402) and the third mounting base (403) are all rectangular plate structures. The length directions of the first mounting base (401) and the second mounting base (402) are perpendicular to the length direction of the supporting top beam (3), and the length direction of the third mounting base (403) is parallel to the length direction of the supporting top beam (3).

6. The shared static testing fixture for multiple aircraft sections as described in claim 5, characterized in that: The first mounting base (401) and the second mounting base (402) are each provided with four fixing holes, which are distributed at the corners. The third mounting base (403) is provided with eight fixing holes, which are symmetrically distributed on the long side of the third mounting base (403).

7. The shared static testing fixture for multiple aircraft sections as described in claim 1, characterized in that: The flat-tail mounting bracket (501) includes a base plate and a side plate. The side plate is vertically fixed on the base plate. The side plate is a rectangular plate with its long side parallel to the base plate. The side plate has two mounting holes from left to right.

8. The shared static testing fixture for multiple aircraft sections as described in claim 1, characterized in that: The section mounting bracket (502) includes a base plate and a side plate. The side plate is vertically fixed on the base plate. The side plate is a rectangular plate with its short side parallel to the base plate. A mounting hole is provided on the side plate.

9. The shared static testing fixture for multiple aircraft sections as described in claim 1, characterized in that: The vertical tail mounting bracket (503) includes a base plate and a side plate. The side plate is vertically fixed on the base plate. The side plate is a long strip plate with its short side parallel to the base plate. The side plate has two mounting holes from top to bottom.

10. A shared static testing fixture for multiple aircraft sections as described in claim 7, 8, or 9, characterized in that: A reinforcing plate is provided between the side plate and the bottom plate.

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